大椭圆轨道卫星交会高轨目标的高精度 视线跟踪控制

摘要/Abstract

摘要： 针对大椭圆轨道卫星交会高轨卫星期间的相对姿态指向控制需求，提出了一种采用混合执行机构的快速、高精度视线跟踪姿态控制的方法.首先根据相对姿态控制流程设计了执行机构的配置，结合采用喷气推力器和角动量交换装置卫星的姿态动力学模型，推导了用相对四元数描述的视线运动学方程.其次，针对交会快速接近段的姿态快速机动要求设计了一种喷气相平面控制律，针对最近交会段的高精度高稳定度视线跟踪要求设计了一种鲁棒滑模控制律.最后设置了一个算例，仿真结果表明：相对距离100 km以内快速交会阶段的视线跟踪控制精度达0.005 3°，从而验证了整套控制算法的有效性.

关键词: 大椭圆轨道, 视线跟踪, 鲁棒滑模控制

Abstract: Focusing on the relative attitude pointing control demand for highly eccentric orbit spacecraft during the period of rendezvous with a HEO target， a kind of agile and highprecision visual tracking attitude control method is proposed, which combines thruster and angular momentum actuators. Firstly， an actuator configuration is designed according to the relative attitude control process. Based on the satellite attitude dynamic models using thruster and angular momentum exchange device as actuators, the visual kinematics equation is derived via relative quaternion method. Secondly, a phase plane jetting control law is designed taking into account the demands for agile attitude maneuver in the rapid approaching phase of rendezvous, a robust sliding mode control law is designed as well, according to the demands for high precision and high stability visual tracking in the final rendezvous phase. Finally, a simulation example is deployed, and the result shows that the precision of visual tracking control within 100 km rapid rendezvous phase reaches 0.005 3°, which validates the effectiveness of the whole control algorithm.

Key words: highly eccentric orbit, visual tracking, robust sliding mode control

徐帷, 武海雷, 卢山, 刘付成. 大椭圆轨道卫星交会高轨目标的高精度视线跟踪控制[J]. 空间控制技术与应用, 2015, 41(2): 6-11.

XU Wei, WU Hai-Lei, LU Shan, LIU Fu-Cheng. A High Precision Attitude Tracking Control Method for Highly Eccentric Orbit Spacecraft Rendezvous with a HEO Target[J]. , 2015, 41(2): 6-11.

参考文献

［1］吕旺,向明江,叶文郁,等. 挠性卫星在轨非约束模态计算研究［J］. 宇航学报, 2014,35(4):404409. LYV W, XIANG M J, YE W Y, et al. Research on calculation of onorbit unconstrained modal of flexible satellite［J］. Journal of Astronautics, 2014,35(4):404409. ［2］刘墩，杨大明.带挠性附件卫星的模型化及截断［J］. 宇航学报, 1989, 10(4):8795. LIU T, YANG D M. Modeling of spacecraft with flexible appendages and model truncation［J］. Journal of Astronautics, 1989,10(4):8795. ［3］刘莹莹，周军. 挠性多体航天器姿态动力学建模与分析［J］.飞行力学，2005,23(3):6063. LIU Y Y, ZHOU J. Dynamics modeling and analysis fora flexible multibody spacecraft［J］. Flight Dynamics, 2005,23(3):6063. ［4］李俊峰，王照林.带挠性伸展附件的航天器姿态动力学研究［J］.清华大学学报(自然科学版)，1996,36(10):3540. LI J F, WANG Z L. Attitude dynamics of a spacecraft with deploying flexible appendages［J］. Journal of Tsinghua University(Sci&Tech), 1996,36(10):3540. ［5］郑钢铁，梁鲁，王光远. 遥感卫星动力学问题系统解决方法和装置［C］// 高分辨率遥感卫星结构振动及控制技术研讨会. 北京：中国宇航学会， 2011：349356 ［6］谈钤,夏惠诚,刘颖，等. 海上舰船电磁频谱规划问题［J］. 火力与指挥控制,2011, 36（7）:197199. TAN Q, XIA H C, LIU Y, et al. Research on navy warship electromagnetic spectrum programming［J］. Fire Control & Command Control 36（7）：197199. ［7］LANDECKER P, GALE M, PENG S, et al. GOES n series data book［R］. California, CDRL PM1103: 2009. ［8］章仁为．卫星轨道姿态动力学与控制［M］．北京：北京航空航天大学出版社，1998：180184. ［9］屠善澄，陈义庆．卫星姿态动力学与控制(1) ［M］．北京：宇航出版社，1999：4973. ［10］曲广吉．航天与力学［M］．北京：中国科学技术出版社，2005：402436. ［11］LIKINS P W. Dynamics and control of flexible space vehicles［R］．Houston City: NASA Technical Report 321329, 1970. ［12］刘暾，赵钧．空间飞行器动力学与控制［M］．哈尔滨：哈尔滨工业大学出版社，2003：240252. ［13］沈毅力, 吕旺, 于永江，等. 用于图像定位与配准的扫描辐射计扫描镜热变形模型研究［J］. 上海航天, 2014(2):2629.